%***********************************************************************
% File: Space1999
% DISE
% Calibration of the model
%***********************************************************************
function Params=Space1999

Params.T        =   250;    % Horizon periods (finite-horizon)
Params.Baseyear =   2023;   % Initial year


%*************************************************************************
%                   Economic model parameters
%*************************************************************************
Params.rho         =       0.015;      % Intertemporal preferences 
Params.sigma       =       1.50;       % Risk aversion parameter
Params.alpha1      =       0.3479;     % Capital technological parameter
Params.alpha2      =       0.0021;     % Satellite technological parameter
Params.deltak      =       0.07;       % Capital depreciation rate
Params.deltas      =       0.15;       % Satellites depreciation rate
%*************************************************************************

%*************************************************************************
%                   Growth rates (technology)
%*************************************************************************
Params.gA0      =       0.015;  % Ititial TFP growth rate
Params.gQ0      =       0.030;  % Initial satellite ISTC growth rate
Params.deltaA   =       0.001;  % Decline in TFP growth rate
Params.deltaQ   =       0.005;  % Decline in satellite ISTC growth rate
%*************************************************************************


%*************************************************************************
%                   Launch cost
%*************************************************************************
Params.gm0      =        0.0;   % Initial launch cost growth rate
Params.deltam   =        0.0;   % Deline in launch cost growth rate
%*************************************************************************


%*************************************************************************
% Initial values for economic variables
%*************************************************************************
y0  =   184.65;
k0  =   555.6987;
s0  =   1.1959;
N0  =   8056;
W0  =   3500;
Z0  =   2050;
F0  =   1030000;
m0  =   0.3;
Params.y0   =   y0;
Params.k0   =   k0;
Params.s0   =   s0;
Params.N0   =   N0;
Params.W0   =   W0;
Params.Z0   =   Z0;
Params.F0   =   F0;

%*************************************************************************
%TFP
%*************************************************************************
T=Params.T;
a(1)=y0/(k0^(Params.alpha1)*s0^(Params.alpha2)*(N0)^(1-Params.alpha1-Params.alpha2));
for i=1:T+350;
    ga(i)=Params.gA0*exp(-Params.deltaA*(i-1));
    a(i+1)=a(i)*exp(ga(i));
end
Params.a=a;

%*************************************************************************
%ISTC
%*************************************************************************
q(1)=1;
for i=1:T+350;
    gq(i)=Params.gQ0*exp(-Params.deltaQ*(i-1));
    q(i+1)=q(i)*exp(gq(i));
end
Params.q=q;

%**************************************************************************
%Population
%**************************************************************************
Params.zita     =   0.05;
N(1)    =   N0;
Ns      =   10200;     
for i=1:T
    N(i+1)=N(i)*(Ns/N(i))^(Params.zita);
end;
for i=T+1:T+350
    N(i)=N(T);
end
Params.N    =   N;
Params.Ns   =   Ns;


%*************************************************************************
%Launch cost
%*************************************************************************
m(1)=m0;
for i=1:T+350;
    m(i+1)=m(i)/(1-Params.gm0*exp(-Params.deltam*(i-1)));
end
Params.m=m;


%*************************************************************************
%                   Space model parameters
%*************************************************************************
Params.theta        =   1.25*10^-10;% Risk of collision
Params.deltaw       =   0.01;       % Dereclit satellites natural decay rate
Params.deltaz       =   0.0015;    % Rocket bodies natural decay rate
Params.deltaf       =   0.0015;    % Fragments natural decay rate
Params.xi           =   0.40;       % Fraction of abandoned derelict satellites
Params.omega        =   4;          % Number of mission related fragments
Params.epsilonw     =   0.001;      % Fraction of breakup of abandoned satellites
Params.epsilonz     =   0.0012;     % Fraction of breakup of body rockets
Params.psi          =   0.60;        % Fraction of abandoned body rockets
Params.phiw         =   44.6;       % Number of fragments from derelict satellite breakups
Params.phiz         =   100.2;      % Number of fragments from rocket bodies breakups
Params.gammas       =   70;         % Number of fragments from satellite collisions
Params.gammaw       =   70;         % Number of fragments from derelict satellite collision
Params.gammaz       =   70;         % Number of fragments from rocket bodies collisions
Params.B1           =   30000;      % Number of objects higher than 10cm (ESA)
Params.B2           =   1000000;    % Number of objects higher than 1cm (ESA)
Params.B3           =   130000000;  % Number of objects higher than 1mm (ESA)
Params.nu1          =   Params.B2/Params.B1;      % Ratio >1cm <10cm to >10cm
Params.nu2          =   Params.B3/Params.B2;      % Ratio >1mm <1cm to >1cm
Params.nu3          =   Params.B3/Params.B1;      % Ratio >1mm to >10cm
Params.eta          =   13.6;         % Satellites per lauch
%*************************************************************************
S0=8500;
%   Mapping parameter
Params.mu      =   S0/s0;    % Mapping parameter

